|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-007/24 F02C-003/00 B64F-001/26|
|미국특허분류(USC)||060/725; 060/039.37; 181/210|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 14 인용 특허 : 28|
One or more Helmholtz-type resonators (270) is/are provided at the junction (260) of a combustor (220) and a combustion chamber (240) of a gas turbine engine (100). In one embodiment, adjacent Helmholtz-type resonators (290, 291, 292), which may be separated by respective baffles (285), have different volumes that help provide for damping different undesired combustion-generated acoustic pressure waves. In some embodiments, a structural member (435) may be provided between adjacent Helmholtz-type resonators (425, 426, 427, 428) at the junction. At least ...
What is claimed is: 1. A can-annular gas turbine engine comprising: a combustor defined by an exterior combustor housing; a combustion chamber defined by an exterior housing and adapted to be joined to the combustor housing at an upstream junction; and a plurality of Helmholtz-type resonators comprising respective cavities at the upstream junction, each of said resonators comprising one or more openings communicating with the combustion chamber, the overall length of each of said openings defining a respective throat length for the respective resonator;...